Gas turbine engine airfoil
In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. Y LE corresponds to a tangential distance from a leading edge to the reference point at a given span position. Y TE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (Y LE −Y d )/(Y d −Y TE ) at 40% span position is about 1.5 and (Y LE −Y d )/(Y d −Y TE ) at 20% span position is about 2.
1. An airfoil for a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve, wherein the airfoil extends from a root, and a zero tangential reference point corresponds to tangential center of the root, Y LE corresponds to a tangential distance from a leading edge to the reference point at a given span position, Y TE corresponds to a tangential distance from a trailing edge to the reference point at the given span position, Y d corresponds to a tangential stacking offset at the given span position, wherein (Y LE −Y d )/(Y d −Y TE ) at 40% span position is 1.5+/−0.10 and (Y LE −Y d )/(Y d −Y TE ) at 20% span position is 2+/−0.10.
2. The airfoil according to claim 1 , wherein (Y LE −Y d )/(Y d −Y TE ) at 100% span position is about 1.1 and (Y LE −Y d )/(Y d −Y TE ) at 90% span position is 1.3+/−0.10.
3. The airfoil according to claim 2 , wherein (Y LE −Y d )/(Y d −Y TE ) at 60% span position is about 1.8 and (Y LE −Y d )/(Y d −Y TE ) at 50% span position is 0.75+/−0.10.
4. The airfoil according to claim 1 , wherein (Y LE −Y d )/(Y d −Y TE ) at 100% span position is about 1 and (Y LE −Y d )/(Y d −Y TE ) at 90% span position is 1.2+/−0.10.
5. The airfoil according to claim 4 , wherein (Y LE −Y d )/(Y d −Y TE ) at 60% span position is about 1.3 and (Y LE −Y d )/(Y d −Y TE ) at 50% span position is 1.4+/−0.10.
6. The airfoil according to claim 1 , wherein (Y LE −Y d )/(Y d −Y TE ) at 100% span position is about 1.1 and (Y LE −Y d )/(Y d −Y TE ) at 90% span position is 1+/−0.10.
7. The airfoil according to claim 6 , wherein (Y LE −Y d )/(Y d −Y TE ) at 60% span position is about 1.4 and (Y LE −Y d )/(Y d −Y TE ) at 50% span position is 1.2+/−0.10.
8. The airfoil according to claim 1 , wherein the airfoil is a fan blade for a gas turbine engine.
9. The airfoil according to claim 1 , wherein (Y LE −Y d )/(Y d −Y TE ) has a tolerance of +/−0.05.
10. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a fan pressure ratio of less than 1.55;
a geared architecture coupling the fan section to the turbine section or the compressor section; and
wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve, wherein the airfoil extends from a root, and a zero tangential reference point corresponds to tangential center of the root, Y LE corresponds to a tangential distance from a leading edge to the reference point at the given span position, Y TE corresponds to a tangential distance from a trailing edge to the reference point at the given span position, Y d corresponds to a tangential stacking offset at the given span position, wherein (Y LE −Y d )/(Y d −Y TE ) at 40% span position is 1.5+/−0.10 and (Y LE −Y d )/(Y d −Y TE ) at 20% span position is 2+/−0.10.
11. The gas turbine engine according to claim 10 , wherein (Y LE −Y d )/(Y d −Y TE ) has a tolerance of +/−0.05.